Gas turbine engine components having internal hybrid cooling cavities

ABSTRACT

Components for gas turbine engines are provided. The components include a hybrid skin core cooling cavity defined by a cold wall and a hot wall, wherein the hot wall is exposed to an exterior environment of the component and a resupply hole is formed in the cold wall and fluidly connects a cold core cavity and the cooling cavity. The resupply hole extends between an inlet on a side of the cold wall exposed to the cold core cavity and an outlet on a side of the cold wall exposed to the cooling cavity. The cavity resupply hole is angled relative to the cold wall at an injection angle such that air passing through the cavity resupply hole is injected into the cooling cavity at the injection angle and at least partially parallel to a direction of flow within the hybrid skin core cooling cavity.

BACKGROUND

Illustrative embodiments pertain to the art of turbomachinery, andspecifically to turbine rotor components.

Gas turbine engines are rotary-type combustion turbine engines builtaround a power core made up of a compressor, combustor and turbine,arranged in flow series with an upstream inlet and downstream exhaust.The compressor compresses air from the inlet, which is mixed with fuelin the combustor and ignited to generate hot combustion gas. The turbineextracts energy from the expanding combustion gas, and drives thecompressor via a common shaft. Energy is delivered in the form ofrotational energy in the shaft, reactive thrust from the exhaust, orboth.

The individual compressor and turbine sections in each spool aresubdivided into a number of stages, which are formed of alternating rowsof rotor blade and stator vane airfoils. The airfoils are shaped toturn, accelerate and compress the working fluid flow, or to generatelift for conversion to rotational energy in the turbine.

Airfoils may incorporate various cooling cavities located adjacentexternal side walls. Such cooling cavities are subject to both hotmaterial walls (exterior or external) and cold material walls (interioror internal). Although such cavities are designed for cooling portionsof the airfoil bodies and exterior hot walls, various cooling flowcharacteristics can cause hot sections where cooling may notsufficiently provide adequate backside convective cooling attributed tolimited cooling flow allocations, resulting in low cavity Reynoldsnumbers and excessive cooling air heat pickup. This may result inreduced local thermal cooling effectiveness. Accordingly, improved meansfor providing more effective cooling within an airfoil may be desirablein order to meet durability life requirements.

BRIEF DESCRIPTION

According to some embodiments, component for gas turbine engines areprovided. The components include a hybrid skin core cooling cavitydefined by a cold wall and a hot wall, wherein the hot wall is exposedto an exterior environment of the component and a hybrid skin corecooling cavity resupply hole formed in the cold wall and fluidlyconnecting a cold core cavity and the hybrid skin core cooling cavity.The hybrid skin core cooling cavity resupply hole extends between aninlet on a side of the cold wall exposed to the cold core cavity and anoutlet on a side of the cold wall exposed to the hybrid skin corecooling cavity. The hybrid skin core cooling cavity resupply hole isangled relative to the cold wall at an injection angle such that airpassing through the hybrid skin core cooling cavity resupply hole isinjected into the hybrid skin core cooling cavity at the injection angleand at least partially parallel to a direction of flow within the hybridskin core cooling cavity.

In addition to one or more of the features described herein, or as analternative, further embodiments of the components may include that thehot wall is an exterior wall of an airfoil and the cold wall is aninterior wall of the airfoil.

In addition to one or more of the features described herein, or as analternative, further embodiments of the components may include that theoutlet of the hybrid skin core cooling cavity resupply hole has ageometric shape that is different from the inlet.

In addition to one or more of the features described herein, or as analternative, further embodiments of the components may include that across-sectional area of the hybrid skin core cooling cavity resupplyhole increases from the inlet to the outlet.

In addition to one or more of the features described herein, or as analternative, further embodiments of the components may include asegmented rib within the hybrid skin core cooling cavity, wherein a gapis formed between segments of the segmented rib.

In addition to one or more of the features described herein, or as analternative, further embodiments of the components may include that atleast one of the inlet and the outlet are positioned within the gapbetween two segments of the segmented rib.

In addition to one or more of the features described herein, or as analternative, further embodiments of the components may include that thesegmented rib divides the hybrid skin core cooling cavity into a firstsubcavity and a second subcavity.

In addition to one or more of the features described herein, or as analternative, further embodiments of the components may include that theoutlet of the hybrid skin core cooling cavity resupply hole is arrangedto supply resupply air into both the first subcavity and the secondsubcavity.

In addition to one or more of the features described herein, or as analternative, further embodiments of the components may include that theoutlet has at least one of a crescent, a curved, and a cusped shape.

In addition to one or more of the features described herein, or as analternative, further embodiments of the components may include that thehybrid skin core cooling cavity resupply hole is a multi-lobed hybridskin core cooling cavity resupply hole.

In addition to one or more of the features described herein, or as analternative, further embodiments of the components may include that themulti-lobed hybrid skin core cooling cavity resupply hole comprises afirst resupply branch and a second resupply branch, wherein each of thefirst resupply branch and the second resupply branch are fluidlyconnected to the inlet and have separate openings at the outlet.

In addition to one or more of the features described herein, or as analternative, further embodiments of the components may include that atleast one lobe of the multi-lobed hybrid skin core cooling cavityresupply hole comprises an internal divider proximate the outlet.

In addition to one or more of the features described herein, or as analternative, further embodiments of the components may include that theoutlet of the hybrid skin core cooling cavity resupply hole isstreamwise diffuser-shaped.

In addition to one or more of the features described herein, or as analternative, further embodiments of the components may include that thehybrid skin core cooling cavity includes a plurality of heat transferaugmentation features.

In addition to one or more of the features described herein, or as analternative, further embodiments of the components may include that theplurality of heat transfer augmentation features are formed on the hotwall of the hybrid skin core cooling cavity.

In addition to one or more of the features described herein, or as analternative, further embodiments of the components may include that theoutlet of the hybrid skin core cooling cavity resupply hole is shaped toalign with a shape of the heat transfer augmentation features.

In addition to one or more of the features described herein, or as analternative, further embodiments of the components may include that theinjection angle is 30° or less.

According to some embodiments, gas turbine engines are provided. The gasturbine engines include a component having a hybrid skin core coolingcavity defined by a cold wall and a hot wall, wherein the hot wall isexposed to an exterior environment of the component and a hybrid skincore cooling cavity resupply hole formed in the cold wall and fluidlyconnecting a cold core cavity and the hybrid skin core cooling cavity.The hybrid skin core cooling cavity resupply hole extends between aninlet on a side of the cold wall exposed to the cold core cavity and anoutlet on a side of the cold wall exposed to the hybrid skin corecooling cavity. The hybrid skin core cooling cavity resupply hole isangled relative to the cold wall at an injection angle such that airpassing through the hybrid skin core cooling cavity resupply hole isinjected into the hybrid skin core cooling cavity at the injection angleand at least partially parallel to a direction of flow within the hybridskin core cooling cavity.

In addition to one or more of the features described herein, or as analternative, further embodiments of the gas turbine engines may includethat the component is one of a blade, a vane, a blade outer air seal, ora combustor panel.

In addition to one or more of the features described herein, or as analternative, further embodiments of the gas turbine engines may includethat the hot wall is an exterior wall of an airfoil, the cold wall is aninterior wall of the airfoil, and the exterior environment is a gas pathof the gas turbine engine.

The foregoing features and elements may be combined in variouscombinations without exclusivity, unless expressly indicated otherwise.These features and elements as well as the operation thereof will becomemore apparent in light of the following description and the accompanyingdrawings. It should be understood, however, the following descriptionand drawings are intended to be illustrative and explanatory in natureand non-limiting.

BRIEF DESCRIPTION OF THE DRAWINGS

The following descriptions should not be considered limiting in any way.With reference to the accompanying drawings, like elements are numberedalike: The subject matter is particularly pointed out and distinctlyclaimed at the conclusion of the specification. The foregoing and otherfeatures, and advantages of the present disclosure are apparent from thefollowing detailed description taken in conjunction with theaccompanying drawings in which like elements may be numbered alike and:

FIG. 1 is a schematic cross-sectional illustration of a gas turbineengine;

FIG. 2 is a schematic illustration of a portion of a turbine section ofthe gas turbine engine of FIG. 1;

FIG. 3A is a schematic illustration of a hybrid skin core cooling cavityconfiguration of an airfoil;

FIG. 3B is a schematic view of a hybrid skin core cooling cavity of theairfoil of FIG. 3A, with a varying height and width along its length;

FIG. 4A is a schematic illustration of an airfoil having a hybrid skincore cooling cavity configuration in accordance with an embodiment ofthe present disclosure;

FIG. 4B is a cross-sectional illustration of the airfoil of FIG. 4A asviewed along the line B-B shown in FIG. 4A;

FIG. 4C is a cross-sectional illustration of the airfoil of FIG. 4A asviewed along the line C-C shown in FIG. 4A;

FIG. 5 is a schematic illustration of a hybrid skin core cooling cavityresupply hole geometry in accordance with an embodiment of the presentdisclosure;

FIG. 6 is a schematic illustration of a hybrid skin core cooling cavityresupply hole geometry in accordance with an embodiment of the presentdisclosure;

FIG. 7 is a schematic illustration of a hybrid skin core cooling cavityresupply hole geometry in accordance with an embodiment of the presentdisclosure;

FIG. 8 is a schematic illustration of a hybrid skin core cooling cavityresupply hole geometry in accordance with an embodiment of the presentdisclosure;

FIG. 9 is a schematic illustration of a hybrid skin core cooling cavityresupply hole geometry in accordance with an embodiment of the presentdisclosure;

FIG. 10 is a schematic illustration of a hybrid skin core cooling cavityresupply hole geometry in accordance with an embodiment of the presentdisclosure; and

FIG. 11 is a schematic illustration of a hybrid skin core cooling cavityresupply hole geometry in accordance with an embodiment of the presentdisclosure.

DETAILED DESCRIPTION

Detailed descriptions of one or more embodiments of the disclosedapparatus and/or methods are presented herein by way of exemplificationand not limitation with reference to the Figures.

FIG. 1 schematically illustrates a gas turbine engine 20. The gasturbine engine 20 is disclosed herein as a two-spool turbofan thatgenerally incorporates a fan section 22, a compressor section 24, acombustor section 26 and a turbine section 28. Alternative engines mightinclude an augmentor section (not shown) among other systems orfeatures. The fan section 22 drives air along a bypass flow path B in abypass duct, while the compressor section 24 drives air along a coreflow path C for compression and communication into the combustor section26 then expansion through the turbine section 28. Although depicted as atwo-spool turbofan gas turbine engine in the disclosed non-limitingembodiment, it should be understood that the concepts described hereinare not limited to use with two-spool turbofans as the teachings may beapplied to other types of turbine engines including three-spoolarchitectures.

The exemplary engine 20 generally includes a low speed spool 30 and ahigh speed spool 32 mounted for rotation about an engine centrallongitudinal axis A relative to an engine static structure 36 viaseveral bearing systems 38. It should be understood that various bearingsystems 38 at various locations may alternatively or additionally beprovided, and the location of bearing systems 38 may be varied asappropriate to the application.

The low speed spool 30 generally includes an inner shaft 40 thatinterconnects a fan 42, a low pressure compressor 44 and a low pressureturbine 46. The inner shaft 40 is connected to the fan 42 through aspeed change mechanism, which in exemplary gas turbine engine 20 isillustrated as a geared architecture 48 to drive the fan 42 at a lowerspeed than the low speed spool 30. The high speed spool 32 includes anouter shaft 50 that interconnects a high pressure compressor 52 and highpressure turbine 54. A combustor 56 is arranged in exemplary gas turbine20 between the high pressure compressor 52 and the high pressure turbine54. An engine static structure 36 is arranged generally between the highpressure turbine 54 and the low pressure turbine 46. The engine staticstructure 36 further supports bearing systems 38 in the turbine section28. The inner shaft 40 and the outer shaft 50 are concentric and rotatevia bearing systems 38 about the engine central longitudinal axis Awhich is collinear with their longitudinal axes.

The core airflow is compressed by the low pressure compressor 44 thenthe high pressure compressor 52, mixed and burned with fuel in thecombustor 56, then expanded over the high pressure turbine 54 and lowpressure turbine 46. The turbines 46, 54 rotationally drive therespective low speed spool 30 and high speed spool 32 in response to theexpansion. It will be appreciated that each of the positions of the fansection 22, compressor section 24, combustor section 26, turbine section28, and fan drive gear system 48 may be varied. For example, gear system48 may be located aft of combustor section 26 or even aft of turbinesection 28, and fan section 22 may be positioned forward or aft of thelocation of gear system 48.

The engine 20 in one example is a high-bypass geared aircraft engine. Ina further example, the engine 20 bypass ratio is greater than about six(6), with an example embodiment being greater than about ten (10), thegeared architecture 48 is an epicyclic gear train, such as a planetarygear system or other gear system, with a gear reduction ratio of greaterthan about 2.3 and the low pressure turbine 46 has a pressure ratio thatis greater than about five. In one disclosed embodiment, the engine 20bypass ratio is greater than about ten (10:1), the fan diameter issignificantly larger than that of the low pressure compressor 44, andthe low pressure turbine 46 has a pressure ratio that is greater thanabout five 5:1. Low pressure turbine 46 pressure ratio is pressuremeasured prior to inlet of low pressure turbine 46 as related to thepressure at the outlet of the low pressure turbine 46 prior to anexhaust nozzle. The geared architecture 48 may be an epicycle geartrain, such as a planetary gear system or other gear system, with a gearreduction ratio of greater than about 2.3:1. It should be understood,however, that the above parameters are only exemplary of one embodimentof a geared architecture engine and that the present disclosure isapplicable to other gas turbine engines including direct driveturbofans.

A significant amount of thrust is provided by the bypass flow B due tothe high bypass ratio. The fan section 22 of the engine 20 is designedfor a particular flight condition—typically cruise at about 0.8 Mach andabout 35,000 feet (10,688 meters). The flight condition of 0.8 Mach and35,000 ft (10,688 meters), with the engine at its best fuelconsumption—also known as “bucket cruise Thrust Specific FuelConsumption (‘TSFC’)”—is the industry standard parameter of lbm of fuelbeing burned divided by lbf of thrust the engine produces at thatminimum point. “Low fan pressure ratio” is the pressure ratio across thefan blade alone, without a Fan Exit Guide Vane (“FEGV”) system. The lowfan pressure ratio as disclosed herein according to one non-limitingembodiment is less than about 1.45. “Low corrected fan tip speed” is theactual fan tip speed in ft/sec divided by an industry standardtemperature correction of [(Tram ° R)/(514.7° R)]^(0.5). The “Lowcorrected fan tip speed” as disclosed herein according to onenon-limiting embodiment is less than about 1150 ft/second (350.5 m/sec).

Although the gas turbine engine 20 is depicted as a turbofan, it shouldbe understood that the concepts described herein are not limited to usewith the described configuration, as the teachings may be applied toother types of engines such as, but not limited to, turbojets,turboshafts, and three-spool (plus fan) turbofans wherein anintermediate spool includes an intermediate pressure compressor (“IPC”)between a low pressure compressor (“LPC”) and a high pressure compressor(“HPC”), and an intermediate pressure turbine (“IPT”) between the highpressure turbine (“HPT”) and the low pressure turbine (“LPT”).

FIG. 2 is a schematic view of a portion of the turbine section 28 thatmay employ various embodiments disclosed herein. Turbine section 28includes a plurality of airfoils 60, 62 including, for example, one ormore blades and vanes. The airfoils 60, 62 may be hollow bodies withinternal cavities defining a number of channels or cores, hereinafterairfoil cores, formed therein and extending between an inner diameter 66and an outer diameter 68, or vice-versa. The airfoil cores may beseparated by partitions within the airfoils 60, 62 that may extendeither from the inner diameter 66 or the outer diameter 68 of theairfoil 60, 62. The partitions may extend for a portion of the length ofthe airfoil 60, 62, but may stop or end prior to forming a complete wallwithin the airfoil 60, 62. Thus, each of the airfoil cores may befluidly connected and form a fluid path within the respective airfoil60, 62. The airfoils 60, 62 may include platforms 70 located proximal tothe inner diameter 66 thereof. Located below the platforms 70 (e.g.,radially inward with respect to the engine axis) may be airflow portsand/or bleed orifices that enable air to bleed from the internalcavities of the airfoils 60, 62. A root of the airfoil may connect to orbe part of the platform 70.

The turbine section 28 is housed within a case 80, which may havemultiple parts (e.g., turbine case, diffuser case, etc.). In variouslocations, components, such as seals, may be positioned between airfoils60, 62 and the case 80. For example, as shown in FIG. 2, blade outer airseals 82 (hereafter “BOAS”) are located radially outward from the blade60. As will be appreciated by those of skill in the art, the BOAS 82 mayinclude BOAS supports that are configured to fixedly connect or attachthe BOAS 82 to the case 80 (e.g., the BOAS supports may be locatedbetween the BOAS 82 and the case 80). As shown in FIG. 2, the case 80includes a plurality of case hooks 84 that engage with BOAS hooks 86 tosecure the BOAS 82 between the case 80 and a tip of the airfoil 60.

As shown and labeled in FIG. 2, a radial direction is upward on the page(e.g., radial with respect to an engine axis) and an axial direction isto the right on the page (e.g., along an engine axis). Thus, radialcooling flows will travel up or down on the page and axial flows willtravel left-to-right (or vice versa).

In a double-wall airfoil (e.g., blade) configuration, thin (i.e., lowaspect ratio) hybrid skin core cavity passages are arranged to extendradially through the airfoil. The hybrid skin core cavity passages areprovided in a thickness direction between the core cooling passages andeach of the pressure and suction side exterior airfoil surfaces.Double-wall cooling has been used as a technology to improve the coolingeffectiveness of various gas turbine engine components, including, butnot limited to, turbine blades, vanes, blade out air seals, combustorpanels, and other hot section components. Often, core support featuresare used to resupply air from a main body core, which creates the corepassages, into the hybrid skin core cavity passages, which creates theskin passages.

With traditional double-wall configurations, a cooling benefit isderived from passing coolant air from the internal radial flow and/orserpentine cavities through the “cold” wall via impingement (resupply)holes and impinging the flow on the “hot” wall. These core support(resupply) features are typically oriented perpendicular to thedirection of flow in the hybrid skin core cooling cavities. Theseperpendicular core supports (resupply) features induce local flowvortices which can generate a significant amount of turbulent mixing tooccur locally within the hybrid skin core cavity passage.

Although the impingement flow field characteristics associated with theresupply holes may appear beneficial, such holes can also create localflow characteristics which are not advantageous from an internal coolingperspective. Adverse impacts due to disruptive impingement resupplyfeatures oriented perpendicular to the streamwise flow direction withinthe hybrid skin core cavity generate pressure and momentum mixing lossesthat may mitigate favorable convective cooling flow fieldcharacteristics. Potential improvements in the internal flow fieldcooling qualities are diminished due to the disruptive nature of theinjection of high pressure and high velocity resupply cooling air flownormal to a main hybrid skin core cooling passage flow direction. Thepotential decrease in bulk fluid cooling temperature may be adverselyimpacted by additional cooling air heat pickup incurred due to highimpingement heat transfer and subsequent heat removal from an exteriorhot wall. In a purely convective hybrid skin core cooling channelpassage, the locally high impingement heat transfer generated by theresupply features oriented normal to the downstream cooling flow mayproduce large local metal temperature gradients that result in locallyhigh thermal strain and subsequent thermal mechanical fatigue crackinitiation and propagation failure mechanisms.

Improving the mixing characteristics of the different flows through theincorporation of “in-line” or “angled” resupply orientation and uniquegeometric features can improve the overall convective coolingcharacteristics of the internal flow field and increase the thermalcooling effectiveness of resupplied hybrid skin core cooling cavitypassages. In accordance with some embodiments of the present disclosure,improvements in the relative alignment of the resupply cooling flow withthe downstream cooling flow within the hybrid skin core cooling channelpassages is achieved. Further, in accordance with some embodiments ofthe present disclosure, the introduction of a resupply cooling flow at amass and momentum flux ratio that is greater than the mass and momentumflux of the downstream cooling flow within the hybrid skin core coolingchannel passage immediately adjacent to the internal surface of the hotexterior airfoil wall can be achieved. By introducing resupply flowthrough a diffused geometric feature (e.g., a geometric resupply hole),the relative mass and momentum mixing of the different flow streams canbe more easily controlled by modifying the expansion ratio of thediffusing section of the resupply geometry.

Turning now to FIGS. 3A-3B, schematic illustrations of an airfoil 300having hybrid skin core cooling cavities located around the periphery ofthe airfoil 300 immediately adjacent to the hot exterior wall surfacesare shown. In some embodiments, it is desirable to locate the hybridskin core cooling cavities in airfoil locations where the external heatflux is the highest in order to mitigate local excessive metaltemperatures observed during engine operation. As a result of the highlocal external heat flux, there may be a significant amount of coolingair temperature rise that occurs due to the high internal heat transferthat is achievable with hybrid skin core cooling cavities. The increasedthermal efficiency associated with the hybrid skin core cavitiesfacilitates the convection of heat from the hot exterior wall to theworking fluid. It is desirable to mitigate cooling air temperature riseand enhance the local internal convective heat transfer which achieves amaximum augmentation level as a function of the ratio of the developmentlength, L, and the hydraulic diameter, D_(h), of the hybrid skin corecooling passage. As the internal flow becomes fully developed, therelative internal heat transfer augmentation begins to decaymonotonically as a function of L/D_(h) for the remainder of the hybridskin core cooling passage, thereby reducing the local thermal coolingeffectiveness. Both of these phenomena can adversely impact the localthermal performance of the hybrid skin core cooling passages. Howeverthese effects can be mitigated through the incorporation of periodicboundary layer restart resupply features within the hybrid skin corecooling cavities, as described herein.

As used herein, a “hybrid skin core cooling cavity” is an internalcavity of an airfoil that has one wall that is a hot wall (e.g.,exterior surface of an airfoil body and exposed to hot, gaspath air,(i.e., an exterior wall exposed to an exterior environment)) and anotherwall that is a cold wall (e.g., a wall that is not exposed to the hotgaspath air, and may be an internal or interior wall structure of theairfoil). For example, as shown in FIG. 3A, the airfoil 300 has twoleading edge hybrid skin core cooling cavities 302, a pressure sidehybrid skin core cooling cavity 304, and a suction side hybrid skin corecooling cavity 306. The hybrid skin core cooling cavities 302, 304, 306,in the present configurations, are arranged around internal cold corecavities 308 of the airfoil 300.

The hybrid skin core cooling cavities 302, 304, 306 are defined in theairfoil 300 with a first wall of the hybrid skin core cooling cavitydefined by an exterior surface wall 310 of the airfoil 300. The exteriorsurface wall 310 is a “hot” wall of the airfoil 300 that is exposed tohot, gaspath air. A second wall of the hybrid skin core cooling cavityis defined by an interior wall 312, with the interior wall 312 being a“cold” wall of the airfoil 300. A “cold” wall is one that is not exposedto the hot gaspath air, and thus remains relatively cool in comparisonto the hot, exterior surface walls. In this illustration, the interiorwalls 312 are defining walls of the internal, cold core cavities 308. Insome arrangements, cooling air can be passed from the cold core cavity308 into an adjacent hybrid skin core cooling cavity 302, 304, 306.

Embodiments described herein are directed to providing double-wallcooling designs, wherein a portion of the cold air within a cold corecavity is directed into a hybrid skin core cooling cavity. In accordancewith embodiments of the present disclosure, the utilization of advanceddouble-wall cooling design configurations that incorporate hybrid skincore cooling channel cavities adjacent to the external airfoil surfacesare used to mitigate cooling flow requirements for high heat loadapplications in order to achieve performance and durability liferequirements. As a result of the relatively small cavity flow areaassociated with hybrid skin core cooling cavities (e.g., “micro”channel) and a relative high flow per unit area, the resulting internalconvective heat transfer is significantly increased.

The hybrid skin core cooling cavities of the present disclosure may havelow hydraulic diameters. For example, with reference to FIG. 3A, thehybrid skin core cooling cavity 304 is shown having a width W that is adistance along the hot or cold wall of the hybrid skin core coolingcavity 304 (e.g., axial or chord-wise direction relative to the airfoil300) and a height H that is a distance or length between the hot walland the cold wall of the hybrid skin core cooling cavity 304 (e.g.,circumferential direction with respect to the airfoil), where the aspectratio of a cooling channel passage is defined as the ratio of the heightH to the width W (H/W).

As shown in FIG. 3B, a schematic view of a hybrid skin core coolingcavity 314 with a varying height and width along its length is shown.The hybrid skin core cooling cavity 314 may be representative of one ormore of the hybrid skin core cooling cavities shown in FIG. 3A. Avariation in hybrid skin core cooling cavity aspect ratio isschematically shown. The height H and/or width W can be varied along thelength (i.e., H1≠H2 and/or W1≠W2 in the radial span-wise and chord-wisedirections). However, some of the hybrid skin core cooling cavities ofthe airfoil 300 may be uniform in dimension, and thus the presentillustrations and description are merely for illustrative andexplanatory purposes, and no limitation is intended.

The hybrid skin core cavities in accordance with embodiments of thepresent disclosure have relatively low cavity aspect ratios H/W and/orvariable aspect ratios along the airfoil span from the inner diameter tothe outer diameter (e.g., root to tip). In some embodiments, a hybridskin core cavity, or portion thereof, may have a height-to-width ratioH/W of less than about 0.8, while conventional cooling passage cavitiesthat extend from the pressure side airfoil surface to suction sideairfoil surface have a height-to-width ratio H/W greater than about 0.8.In some embodiments, the hybrid skin core cavities 302, 304, 306 of theairfoil 300 can have a height-to-width H/W ratio of 0.8 or less along atleast a portion of a radial length of the hybrid skin core cavitycooling passage. As noted above, as used with respect to the describedcavity height-to-width ratio, a “height” of a cavity is a distance froma surface on an outer wall of the airfoil that partially defines thecavity to a surface of an inner wall that is internal to the airfoil(e.g., as shown in FIG. 3A, a distance between a hot wall 310 and a coldwall 312 that define the hybrid skin core cavities 302, 304, 306).Further, a width of a cavity, as used herein, is an arc length of thecold wall 312.

As shown in FIG. 3A, the hybrid skin core cavity cooling passages 304,306 may be provided in the airfoil pressure and suction walls, whichseparate the respective airfoil walls into the hot side wall 310 and thecold side wall 312. The hybrid skin core cavity cooling passages 302,304, 304 typically have a much lower aspect ratio H/W than the “centralmain-body core” passages 308. Typically, hybrid skin core cavity coolingpassages have a cavity height H to cavity width W ratio H/W that mayvary in cavity aspect ratio between 3:1≥H/W≥1:5. The height of thehybrid skin core cavities 304, 306 are generally in the thicknessdirection and typically normal to a tangent line L at the exteriorairfoil hot surface 310, and is in a range of 0.010-0.200 inches(0.25-5.08 mm). In some situations, the length to hydraulic diameterL/D_(h) of the hybrid skin core cooling cavities can be excessively highL/D_(h)>15. Such hybrid skin core cooling cavities may be referred toherein as “micro” channels or “hybrid micro cooling channel cavities.”

In convectively cooled hybrid micro cooling channel cavities theinternal cooling flow has a development flow length, L/D_(h), in whichthe internal convective heat transfer increases to a maximumaugmentation level. Once the internal cooling flow in the micro coolingchannel cavity is fully developed the internal convective heat transferaugmentation begins to decrease monotonically as a function of L/D_(h)for the remainder of the hybrid skin core cooling micro channel length.As a result of the high internal convective heat transfer within thehybrid micro cooling channel there may be a significant amount offrictional pressure loss and cooling air temperature heat pickup thatoccurs. Both of these effects adversely can impact the local thermalcooling capacity of the hybrid micro cooling channels.

In order to mitigate excessive pressure loss and cooling air temperatureheat pickup, it may be desirable to alleviate the internal flowcharacteristics that adversely impact the local convective coolingeffectiveness that occurs in a long L/D_(h) hybrid micro cooling channelcavity. In accordance with embodiments provided herein, means formitigating reductions in convective heat transfer augmentation resultingfrom fully developed flow, excessive pressure loss, and cooling airtemperature heat pickup in high L/D_(h) hybrid micro cooling channelsinclude the incorporation of boundary layer restart resupply features orlow momentum mixing resupply features, hereinafter “hybrid skin corecooling cavity resupply holes.”

The hybrid skin core cooling cavity resupply holes are geometricresupply holes that fluidly connect a cold “central main-body” corecavity with a hybrid skin core cooling cavity. In some embodiments, thehybrid skin core cooling cavity resupply holes may be formed such thatair passing through the hybrid skin core cooling cavity resupply holesexits normal to the cold wall and may impinge upon the hot wall. Sucharrangement may be limited by a method of manufacture. In someembodiments, the hybrid skin core cooling cavity resupply holes may beangled relative to the cold wall and may be manufactured using additivemanufacturing and/or fugitive core techniques. In some embodiments, thehybrid skin core cooling cavity resupply holes can be located betweenradially extending segmented rib features located within a hybrid skincore cooling cavity and/or segregating two adjacent hybrid skin corecooling cavities. In some embodiments, the hybrid skin core coolingcavity resupply holes can be formed within a cold wall of a singlehybrid skin core cooling cavity.

Turning to FIGS. 4A-4C, schematic illustrations of an airfoil 400 inaccordance with an embodiment of the present disclosure are shown. Theairfoil 400 includes a plurality of hybrid skin core cooling cavities414 and interior cold core cavities 416. FIGS. 4B-4C illustratecross-sectional views of one of the hybrid skin core cooling cavities414, as indicated in FIG. 4A. The hybrid skin core cooling cavity 414 isdefined between a hot wall 418 and a cold wall 420, with the cold wall420 being a wall of one of the cold core cavities 416, as shown. Thehybrid skin core cooling cavity 414 can be sub-divided or separated byone or more radially extending segmented ribs 432. The cold corecavities 416 can be fluidly connected to the hybrid skin core coolingcavities 414 by one or more hybrid skin core cooling cavity resupplyholes 426. As shown in FIGS. 4B-4C, various cooling features are formedrelative to the hybrid skin core cooling cavity 414, such as within thehot and cold walls 418, 420.

For example, with reference to FIG. 4B, the hot wall 418 includes aplurality of film cooling holes 422 which are arranged to direct airfrom within the hybrid skin core cooling cavity 414 into the gas pathand to form a film of air on the exterior surface of the hot wall 418.Further, as shown, the hot wall 418 can include various heat transferaugmentation features 424, such as turbulators, trip strips, including,but not limited to: normal, skewed, segmented skewed, chevron, segmentedchevron, W-shaped, discrete W's, pin fins, hemispherical bumps and/ordimples, as well as non-hemispherical shaped bumps and/or dimples, etc.

The hybrid skin core cooling cavity 414 is resupplied with cool air fromthe cold core cavity 416 through a plurality of hybrid skin core coolingcavity resupply holes 426. Each hybrid skin core cooling cavity resupplyhole 426 extends from an inlet 428 to an outlet 430, with the inlet 428being open to the cold core cavity 416 and the outlet 430 being open tothe hybrid skin core cooling cavity 414. The hybrid skin core coolingcavity resupply holes 426 are angled relative to the cold wall 420 at aninjection angle α. In some embodiments, the injection angle α may be 30°or less. The injection angle α may be selected to achieve low momentummixing between the resupply air provided from the cold core cavity 416and the air within the hybrid skin core cooling cavity 414. Theinjection angle α is an angle for injection of resupply air passing fromthe cold core cavity 416, through the hybrid skin core cooling cavityresupply hole 426, and into the hybrid skin core cooling cavity 414 suchthat the injected air is directed, at least partially, parallel to adirection of flow within the hybrid skin core cooling cavity 414.

FIG. 4C illustrates an elevation view of a portion of the hybrid skincore cooling cavity 414 having a plurality of radially extendingsegmented ribs 432. The radially extending segmented ribs 432 can dividethe hybrid skin core cooling cavity 414 into a plurality of subcavities.In some embodiments, the radially extending segmented ribs 432 may beemployed to partially separate two adjacent hybrid skin core coolingcavities, rather than subdividing a single hybrid skin core coolingcavity. As described herein, a first hybrid skin core cooling cavity 414a is shown adjacent a second hybrid skin core cooling cavity 414 b (withthe hybrid skin core cooling cavities 414 a, 414 b referring to eitheradjacent hybrid skin core cooling cavities or subcavities divided by theribs 432). The segmented ribs 432 are divided by rib gaps 434. As shown,the hybrid skin core cooling cavity resupply hole 426 is located withinthe rib gap 434 between segments of a segmented rib 432.

As shown in FIG. 4C, the outlet 430 of the hybrid skin core coolingcavity resupply hole 426 has a geometric shape such that air flowingthrough the hybrid skin core cooling cavity resupply hole 426 will enterboth the first and second hybrid skin core cooling cavities 414 a, 414b. Further, as shown, the inlet 428 is shown with a smallercross-sectional area than the outlet 430 (in this case the inlet 428 iscircular and the outlet 430 is crescent shaped or cusped). As such, thecross-sectional area of the hybrid skin core cooling cavity resupplyhole 426 increases from the inlet 428 to the outlet 430. The increase incross-sectional area may be continuous or step-wise, and in someembodiments, only a portion of the hybrid skin core cooling cavityresupply hole may have an increasing cross-section area (e.g., aconstant cross-sectional area for a length of the hybrid skin corecooling cavity resupply hole and a changing cross-sectional area foranother length of the hybrid skin core cooling cavity resupply hole). Insome embodiments, the inlet 428 may be elliptical with a long axisextending in a radial direction (e.g., in the direction of flowindicated in FIG. 4B). Further, as shown, and in some embodiments, theinlet and the outlet may have different geometric shapes.

The hybrid skin core cooling cavity resupply holes, and particularly theoutlet thereof, may have various geometric shapes, orientations at theinlet, orientations at the outlet, and/or orientations/shapes for thelength of the hybrid skin core cooling cavity resupply hole between theinlet and the outlet thereof. In some embodiments, the arrangement ofthe hybrid skin core cooling cavity resupply hole may be linear and/orcurvilinear in shape. The hybrid skin core cooling cavity resupply holesmay be either single or multi-lobed geometric shapes at the outlet, inorder to promote local changes in the flow vortices which can alter andrestart the thermal, momentum, and viscous boundary layers along arib-roughened surface adjacent to the hot external airfoil wall. In someembodiments, the outlet of the hybrid skin core cooling cavity resupplyhole may comprises two or more openings, with different resupplybranches extending from a single inlet opening to multiple outletopenings.

The unique shapes of the hybrid skin core cooling cavity resupply holesand relative orientation to a cooling flow flowing through the hybridskin core cooling cavity (e.g., upward direction arrows shown in FIG.4B) may be dependent on various turbulator (e.g., trip strips)geometries incorporated within the hybrid skin core cooling cavities.For example, trip strip geometries including normal, skewed, segmentedskewed, single chevron, segmented chevron, W-shaped, etc. may eachrequire a unique geometric shape of the outlets of the hybrid skin corecooling cavity resupply holes in order to induce local vortices that canreinitialize near-wall thermal, momentum, and viscous boundary layers.Because the vortex structures produced by each of the trip stripgeometry orientations are inherently different with the hybrid skin corecooling cavities, the flow vortex structures required to restart athermal boundary layer while minimizing momentum mixing losses betweeninjected resupply flow through the hybrid skin core cooling cavityresupply holes and the cooling flow within the hybrid skin core coolingcavity may need to consist of uniquely defined geometric single and/ormulti-lobed geometric features, orientations, and injection angles.

Various embodiments provided herein are directed to identifying anddefining unique geometries for hybrid skin core cooling cavity resupplyholes that may be required in order to address adverse reductions inconvective heat transfer augmentation resulting from fully developedflow, excessive pressure loss, and cooling air temperature heat pickupin high L/D_(h) hybrid skin core cooling cavities. As such, the hybridskin core cooling cavity resupply holes can operate as boundary layerrestart resupply, wherein the cooling flow within the hybrid skin corecooling cavities can be resupplied and additional cool air and/orpressure can be injected into the hybrid skin core cooling cavitynecessary to improve convective cooling characteristics and overallthermal performance of hybrid skin core cooling cavities.

Turning now to FIGS. 5-10, schematic illustrations of non-limitingexamples of geometries of hybrid skin core cooling cavity resupply holesin accordance with the present disclosure are shown. In addition toillustrating the geometry of the hybrid skin core cooling cavityresupply holes, FIGS. 5-10 also illustrate an arrangement of heattransfer augmentation features for the respective airfoils, with theheat transfer augmentation features being located on a hot wall of thehybrid skin core cooling cavities. The hybrid skin core cooling cavityresupply holes shown in FIGS. 5-10 are formed passing through a coldwall of the hybrid skin core cooling cavities, similar to that shown anddescribed above.

FIG. 5 illustrates a partial illustration of an airfoil 500 having aplurality of segmented ribs 532 separating two adjacent hybrid skin corecooling cavities 514 a, 514 b, with a plurality of heat transferaugmentation features 524 located on a hot wall of the hybrid skin corecooling cavities 514 a, 514 b. The airfoil 500 further includes a hybridskin core cooling cavity resupply hole 526 located between two of thesegmented ribs 532 (e.g., within a gap of two radially adjacent ribsegments) and passing through a cold wall of the hybrid skin corecooling cavities 514 a, 514 b. The hybrid skin core cooling cavityresupply hole 526 includes a first resupply branch 536 and a secondresupply branch 538. In this embodiment, a single inlet opening isarranged to supply cool air from a cold core cavity into the hybrid skincore cooling cavities 514 a, 514 b, with a portion of the air passingthrough the first resupply branch 536 into a first hybrid skin corecooling cavity 514 a and a portion of the air passing through the secondresupply branch 538 into a second hybrid skin core cooling cavity 514 b.The openings of the resupply branches 536, 538 at the outlet of thehybrid skin core cooling cavity resupply hole 526 can have variousgeometric shapes to provide a desired injection of air into the hybridskin core cooling cavities 514 a, 514 b. For example, in theillustration of FIG. 5, the openings of the resupply branches 536, 538at the outlet may be elongated ovals or ellipses with the long axisextending substantially radially or parallel with a flow direction ofair within the respective hybrid skin core cooling cavities 514 a, 514b. In this illustration, the first and second resupply branches 536, 538are lobed in shape. Lobed or multi-lobed branches may be curved orrounded, and in some embodiments, the lobe of a branch may transitioninto the geometric shape of the outlet of the respective lobe or branch.

FIG. 6 illustrates a partial illustration of an airfoil 600 having aplurality of segmented ribs 632 separating two adjacent hybrid skin corecooling cavities 614 a, 614 b, with a plurality of heat transferaugmentation features 624 located on a hot wall of the hybrid skin corecooling cavities 614 a, 614 b. The airfoil 600 further includes a hybridskin core cooling cavity resupply hole 626 located between two of thesegmented ribs 632 (e.g., within a gap of two radially adjacent ribsegments) and passing through a cold wall of the hybrid skin corecooling cavities 614 a, 614 b. The hybrid skin core cooling cavityresupply hole 626 includes a first resupply branch 636 and a secondresupply branch 638. Similar to the embodiment of FIG. 5, a single inletopening is arranged to supply cool air from a cold core cavity into thehybrid skin core cooling cavities 614 a, 614 b, with a portion of theair passing through the first resupply branch 636 into a first hybridskin core cooling cavity 614 a and a portion of the air passing throughthe second resupply branch 638 into a second hybrid skin core coolingcavity 614 b. The openings of the resupply branches 636, 638 at theoutlet of the hybrid skin core cooling cavity resupply hole 626 can havevarious geometric shapes to provide a desired injection of air into thehybrid skin core cooling cavities 614 a, 614 b. For example, in theillustration of FIG. 6, the openings of the resupply branches 636, 638at the outlet may be elongated curves. In this illustration, the firstand second resupply branches 636, 638 are curved or arcuate in shape.

FIG. 7 illustrates a partial illustration of an airfoil 700 having aplurality of segmented ribs 732 separating two adjacent hybrid skin corecooling cavities 714 a, 714 b, with a plurality of heat transferaugmentation features 724 located on a hot wall of the hybrid skin corecooling cavities 714 a, 714 b. The airfoil 700 further includes a hybridskin core cooling cavity resupply hole 726 located between two of thesegmented ribs 732 (e.g., within a gap of two radially adjacent ribsegments) and passing through a cold wall of the hybrid skin corecooling cavities 714 a, 714 b. The hybrid skin core cooling cavityresupply hole 726 includes a first resupply branch 736 and a secondresupply branch 738. Similar to the embodiments described above, asingle inlet opening is arranged to supply cool air from a cold corecavity into the hybrid skin core cooling cavities 714 a, 714 b, with aportion of the air passing through the first resupply branch 736 into afirst hybrid skin core cooling cavity 714 a and a portion of the airpassing through the second resupply branch 738 into a second hybrid skincore cooling cavity 714 b. The openings of the resupply branches 736,738 at the outlet of the hybrid skin core cooling cavity resupply hole726 are split-shape. In this illustration, the first and second resupplybranches 736, 738 are curved or arcuate in shape. The split-shapeopenings of the resupply branches 736, 738 are arranged to align ormirror the shape or geometry of the heat transfer augmentation features724, and thus can provide a specific injection of cool resupply air intothe hybrid skin core cooling cavities 714 a, 714 b. The split-shape ofthe opening can encourage diffusion of the cool resupply flow into thehybrid skin core cooling cavities 714 a, 714 b to thus minimize vorticesas the resupply air is injected into a flow stream within the hybridskin core cooling cavities 714 a, 714 b.

FIG. 8 illustrates a partial illustration of an airfoil 800 having aplurality of segmented ribs 832 separating two adjacent hybrid skin corecooling cavities 814 a, 814 b, with a plurality of heat transferaugmentation features 824 located on a hot wall of the hybrid skin corecooling cavities 814 a, 814 b. The airfoil 800 further includes a hybridskin core cooling cavity resupply hole 826 located between two of thesegmented ribs 832 (e.g., within a gap of two radially adjacent ribsegments) and passing through a cold wall of the hybrid skin corecooling cavities 814 a, 814 b. The hybrid skin core cooling cavityresupply hole 826 includes a first resupply branch 836 and a secondresupply branch 838. Similar to the embodiments described above, asingle inlet opening is arranged to supply cool air from a cold corecavity into the hybrid skin core cooling cavities 814 a, 814 b, with aportion of the air passing through the first resupply branch 836 into afirst hybrid skin core cooling cavity 814 a and a portion of the airpassing through the second resupply branch 838 into a second hybrid skincore cooling cavity 814 b. The openings of the resupply branches 836,838 at the outlet of the hybrid skin core cooling cavity resupply hole826 are split-shape, similar to the arrangement shown in FIG. 7.However, in this embodiment, the resupply branches 836, 838 includeinternal dividers 840, 842 arranged to split a flow within the resupplybranches 836, 838. In this illustration, the first and second resupplybranches 836, 838 are curved or arcuate in shape with the split-shaped(and divided) openings at the outlets thereof. Similar to the embodimentof FIG. 7, the split-shape openings of the resupply branches 836, 838are arranged to align or mirror the shape or geometry of the heattransfer augmentation features 824, and thus can provide a specificinjection of cool resupply air into the hybrid skin core coolingcavities 814 a, 814 b.

FIG. 9 illustrates a partial illustration of an airfoil 900 having aplurality of segmented ribs 932 separating two adjacent hybrid skin corecooling cavities 914 a, 914 b, with a plurality of heat transferaugmentation features 924 located on a hot wall of the hybrid skin corecooling cavities 914 a, 914 b. The airfoil 900 further includes a hybridskin core cooling cavity resupply hole 926 located between two of thesegmented ribs 932 (e.g., within a gap of two radially adjacent ribsegments) and passing through a cold wall of the hybrid skin corecooling cavities 914 a, 914 b. The hybrid skin core cooling cavityresupply hole 926 includes a first resupply branch 936 and a secondresupply branch 938. Similar to the embodiments described above, asingle inlet opening is arranged to supply cool air from a cold corecavity into the hybrid skin core cooling cavities 914 a, 914 b. Aportion of the air passing through the first resupply branch 936 into afirst hybrid skin core cooling cavity 914 a and a portion of the airpassing through the second resupply branch 938 into a second hybrid skincore cooling cavity 914 b. The openings of the resupply branches 936,938 at the outlet of the hybrid skin core cooling cavity resupply hole926 are streamwise diffuser-shaped. In this illustration, the first andsecond resupply branches 936, 938 are curved or arcuate in shape withthe streamwise diffuser-shaped openings at the outlets thereof.

FIG. 10 illustrates a partial illustration of an airfoil 1000 having aplurality of segmented ribs 1032 separating two adjacent hybrid skincore cooling cavities 1014 a, 1014 b, with a plurality of heat transferaugmentation features 1024 located on a hot wall of the hybrid skin corecooling cavities 1014 a, 1014 b. The airfoil 1000 further includes ahybrid skin core cooling cavity resupply hole 1026 located between twoof the segmented ribs 1032 (e.g., within a gap of two radially adjacentrib segments) and passing through a cold wall of the hybrid skin corecooling cavities 1014 a, 1014 b. The hybrid skin core cooling cavityresupply hole 1026 includes a first resupply branch 1036 and a secondresupply branch 1038. Similar to the embodiments described above, asingle inlet opening is arranged to supply cool air from a cold corecavity into the hybrid skin core cooling cavities 1014 a, 1014 b. Aportion of the air passing through the first resupply branch 1036 into afirst hybrid skin core cooling cavity 1014 a and a portion of the airpassing through the second resupply branch 1038 into a second hybridskin core cooling cavity 1014 b. The openings of the resupply branches1036, 1038 at the outlet of the hybrid skin core cooling cavity resupplyhole 1026 are angled (e.g., parallel with a direction of the heattransfer augmentation features 1024) and include internal dividers 1040,1042 arranged to split a flow within the resupply branches 1036, 1038.In this illustration, the first and second resupply branches 1036, 1038are curved or arcuate in shape with the angled (and divided) openings atthe outlets thereof.

The above described embodiments are shown with segmented ribs dividingtwo adjacent hybrid skin core cooling cavities and the hybrid skin corecooling cavity resupply holes are positioned at locations in gaps of thesegmented ribs. However, the present disclosure is not so limited. Forexample, in some embodiments, the hybrid skin core cooling cavityresupply hole can be located on a cold wall of a single hybrid skin corecooling cavity.

Turning now to FIG. 11, one such example arrangement of an airfoil 1100having a hybrid skin core cooling cavity resupply hole 1126 positionedin the center area of a hybrid skin core cooling cavity 1114. As shown,an inlet 1128 is formed in a cold wall of the hybrid skin core coolingcavity 1114 with resupply branches 1136, 1138 extending through the coldwall to an outlet 1130, thus defining the hybrid skin core coolingcavity resupply hole 1126. The outlet 1130 is formed in two parts, withopenings at the ends of the respective resupply branches 1136, 1138.Each of the openings of the outlet 1130 include internal dividers 1140,1142 The openings of the outlet 1130 are angled to align with thegeometry of heat transfer augmentation features 1124 that are located ona hot wall of the hybrid skin core cooling cavity 1114.

Although described herein with respect to an airfoil, those of skill inthe art will appreciate that embodiments provided herein can be appliedto various double-walled cooling passages. For example, embodimentsprovided herein can be applied to blades, vanes, blade outer air seals,combustor hot section components, etc. without departing from the scopeof the present disclosure. Advantageously, design concepts for suchcomponents that incorporate long L/D_(h) hybrid micro channel coolingcavities can implement boundary layer restart resupply geometryfeatures, as described herein, to mitigate design challenges associatedwith large pressure loss, extreme cooling air temperature heat pickup,and reduction in heat transfer augmentation due to long L/D_(h) fullydeveloped flow fields.

The geometry and shapes of the hybrid skin core cooling cavity resupplyholes disclosed herein can be formed, in some embodiments, directlyusing metal powder base fusion additive manufacturing processes. In someembodiments, the hybrid skin core cooling cavity resupply holes can becreated by using additive manufacturing processes (e.g., fabricatedceramic alumina or silica cores) from which conventional lost waxinvestment casting processes may be used to create single crystal blade,vane, blade outer air seal, combustor panel, etc. cooling designconfiguration. Further, in some embodiments, the hybrid skin corecooling cavity resupply holes can be created using fugitive coremanufacturing fabrication processes.

Although the various above embodiments are shown as separateillustrations, those of skill in the art will appreciate that thevarious features can be combined, mix, and matched to form an airfoilhaving a desired cooling scheme that is enabled by one or more featuresdescribed herein. Thus, the above described embodiments are not intendedto be distinct arrangements and structures of airfoils and/or corestructures, but rather are provided as separate embodiments for clarityand ease of explanation.

Advantageously, embodiments provided herein are directed to airfoilcooling cavities having improved cooling features. Further,advantageously, improved part life, improved cooling, and reduced weightcan all be achieved from embodiments of the present disclosure.

As used herein, the term “about” is intended to include the degree oferror associated with measurement of the particular quantity based uponthe equipment available at the time of filing the application. Forexample, “about” may include a range of ±8%, or 5%, or 2% of a givenvalue or other percentage change as will be appreciated by those ofskill in the art for the particular measurement and/or dimensionsreferred to herein.

The terminology used herein is for the purpose of describing particularembodiments only and is not intended to be limiting of the presentdisclosure. As used herein, the singular forms “a,” “an,” and “the” areintended to include the plural forms as well, unless the context clearlyindicates otherwise. It will be further understood that the terms“comprises” and/or “comprising,” when used in this specification,specify the presence of stated features, integers, steps, operations,elements, and/or components, but do not preclude the presence oraddition of one or more other features, integers, steps, operations,element components, and/or groups thereof. It should be appreciated thatrelative positional terms such as “forward,” “aft,” “upper,” “lower,”“above,” “below,” “radial,” “axial,” “circumferential,” and the like arewith reference to normal operational attitude and should not beconsidered otherwise limiting.

While the present disclosure has been described with reference to anillustrative embodiment or embodiments, it will be understood by thoseskilled in the art that various changes may be made and equivalents maybe substituted for elements thereof without departing from the scope ofthe present disclosure. In addition, many modifications may be made toadapt a particular situation or material to the teachings of the presentdisclosure without departing from the essential scope thereof.Therefore, it is intended that the present disclosure not be limited tothe particular embodiment disclosed as the best mode contemplated forcarrying out this present disclosure, but that the present disclosurewill include all embodiments falling within the scope of the claims.

What is claimed is:
 1. A component for a gas turbine engine, thecomponent comprising: a hybrid skin core cooling cavity defined by acold wall and a hot wall, wherein the hot wall is exposed to an exteriorenvironment of the component; and a hybrid skin core cooling cavityresupply hole formed in the cold wall and fluidly connecting a cold corecavity and the hybrid skin core cooling cavity, wherein the hybrid skincore cooling cavity resupply hole extends between an inlet on a side ofthe cold wall exposed to the cold core cavity and an outlet on a side ofthe cold wall exposed to the hybrid skin core cooling cavity, andwherein the hybrid skin core cooling cavity resupply hole is angledrelative to the cold wall at an injection angle such that air passingthrough the hybrid skin core cooling cavity resupply hole is injectedinto the hybrid skin core cooling cavity at the injection angle and atleast partially parallel to a direction of flow within the hybrid skincore cooling cavity.
 2. The component of claim 1, wherein the hot wallis an exterior wall of an airfoil and the cold wall is an interior wallof the airfoil.
 3. The component of claim 1, wherein the outlet of thehybrid skin core cooling cavity resupply hole has a geometric shape thatis different from the inlet.
 4. The component of claim 1, wherein across-sectional area of the hybrid skin core cooling cavity resupplyhole increases from the inlet to the outlet.
 5. The component of claim1, further comprising a segmented rib within the hybrid skin corecooling cavity, wherein a gap is formed between segments of thesegmented rib.
 6. The component of claim 5, wherein at least one of theinlet and the outlet are positioned within the gap between two segmentsof the segmented rib.
 7. The component of claim 5, wherein the segmentedrib divides the hybrid skin core cooling cavity into a first subcavityand a second subcavity.
 8. The component of claim 7, wherein the outletof the hybrid skin core cooling cavity resupply hole is arranged tosupply resupply air into both the first subcavity and the secondsubcavity.
 9. The component of claim 1, wherein the outlet has at leastone of a crescent, a curved, and a cusped shape.
 10. The component ofclaim 1, wherein the hybrid skin core cooling cavity resupply hole is amulti-lobed hybrid skin core cooling cavity resupply hole.
 11. Thecomponent of claim 10, wherein the multi-lobed hybrid skin core coolingcavity resupply hole comprises a first resupply branch and a secondresupply branch, wherein each of the first resupply branch and thesecond resupply branch are fluidly connected to the inlet and haveseparate openings at the outlet.
 12. The component of claim 10, whereinat least one lobe of the multi-lobed hybrid skin core cooling cavityresupply hole comprises an internal divider proximate the outlet. 13.The component of claim 1, wherein the outlet of the hybrid skin corecooling cavity resupply hole is streamwise diffuser-shaped.
 14. Thecomponent of claim 1, wherein the hybrid skin core cooling cavityincludes a plurality of heat transfer augmentation features.
 15. Thecomponent of claim 14, wherein the plurality of heat transferaugmentation features are formed on the hot wall of the hybrid skin corecooling cavity.
 16. The component of claim 14, wherein the outlet of thehybrid skin core cooling cavity resupply hole is shaped to align with ashape of the heat transfer augmentation features.
 17. The component ofclaim 1, wherein the injection angle is 30° or less.
 18. A gas turbineengine comprising: a component having a hybrid skin core cooling cavitydefined by a cold wall and a hot wall, wherein the hot wall is exposedto an exterior environment of the component and a hybrid skin corecooling cavity resupply hole formed in the cold wall and fluidlyconnecting a cold core cavity and the hybrid skin core cooling cavity,wherein the hybrid skin core cooling cavity resupply hole extendsbetween an inlet on a side of the cold wall exposed to the cold corecavity and an outlet on a side of the cold wall exposed to the hybridskin core cooling cavity, and wherein the hybrid skin core coolingcavity resupply hole is angled relative to the cold wall at an injectionangle such that air passing through the hybrid skin core cooling cavityresupply hole is injected into the hybrid skin core cooling cavity atthe injection angle and at least partially parallel to a direction offlow within the hybrid skin core cooling cavity.
 19. The gas turbineengine of claim 18, wherein the component is one of a blade, a vane, ablade outer air seal, or a combustor panel.
 20. The gas turbine engineof claim 18, wherein: the hot wall is an exterior wall of an airfoil,the cold wall is an interior wall of the airfoil, and the exteriorenvironment is a gas path of the gas turbine engine.